Gas turbine vane assembly seal and support system

Abstract

Apparatus for statically determinant mounting of a vane assembly in a gas turbine engine includes means for assuring contact support of the vane assembly in a predetermined number of identified locations. The vane assembly includes at least one vane extending between a radially outer nozzle band and a radially inner nozzle band. The radially outer nozzle band has axially directed load bearing elements on distal ends. The radially inner nozzle band has a radially inwardly oriented flange depending therefrom. The engine includes a radially outer support member positioned to engage the load bearing elements in the radially outer nozzle band when the vane assembly is in an operative position. A radially inner support member is incorporated in the engine for engaging the flange to axially restrain the vane assembly. The inner support member includes means for releasably connecting the flange thereto for supporting the vane assembly in radially and circumferential directions. Both the inner nozzle band and outer nozzle band have seals associated therewith for inhibiting gas flow between the respective nozzle band and the adjacent supporting members.

What is claimed is: 
     
       1. Apparatus for statically determinant mounting of a vane assembly in a gas turbine engine, the vane assembly including at least one vane extending between a radially outer nozzle band and a radially inner nozzle band, the radially outer nozzle band having axially directed load bearing elements on distal ends thereof and the radially inner nozzle band having a radially inward oriented flange depending therefrom, the engine including a radially outer support member positioned to engage the load bearing elements in the radially outer nozzle band when the vane assembly is in an operative position and further including a radially inner support member for engaging the flange to axially restrain the vane assembly, the inner support member including means for releasably connecting the flange thereto for supporting the vane assembly in radial and circumferential directions and further including seal means operatively coupled between said radially outer nozzle band and said radially outer support member for inhibiting gas flow therebetween, the seal means including a radially outwardly extending flange connected to said radially outer nozzle band and a corresponding flange extending from the engine substantially parallel to said radially outwardly extending flange, a resilient seal being positioned between said radially outwardly extending flange and said corresponding flange. 
     
     
       2. The apparatus of claim 1 and including seal means operatively coupled between said inner nozzle band and said inner support for inhibiting gas flow therebetween. 
     
     
       3. The apparatus of claim 1 wherein said connecting means comprises at least a first and a second bolt passing through a respective one of a pair of spaced apertures in said radially inner support member, said apertures in said flange being sized to slide on said bolts to provide axial motion of said vane assembly. 
     
     
       4. The apparatus of claim 3 and including bushings in each of said apertures in said flange for slidably mating with said bolts and provides a controlled spacing for supporting said flange for pivotable motion. 
     
     
       5. The apparatus of claim 2 wherein said seal means comprises a radially extending flange on said inner support member substantially parallel to said flange on said inner nozzle band and a resilient seal position between said support member flange and said nozzle band flange. 
     
     
       6. The apparatus of claim 4 wherein said bushings and said apertures in said flange are cooperative when said vane assembly is in an assembled position to accommodate axial motion of said vane assembly and provide for a controlled degree of tilting of said vane assembly about said flange. 
     
     
       7. The apparatus of claim 1 wherein said connecting means comprises a tongue and groove coupling between said flange and said radially inner support member. 
     
     
       8. Apparatus for inhibiting gas leakage about a vane assembly in a gas flow path in a gas turbine engine, the vane assembly having at least one vane extending between a radially outer and a radially inner nozzle band assembly, the radially outer nozzle band assembly having at least one bearing surface facing axially aft for supporting the outer nozzle band axially against pressure asserted by gas in the gas flow path, the engine including an outer support member having a load bearing surface for mating with the bearing surface on the outer nozzle band assembly, each of the outer nozzle band assembly and the outer support member including sealing surfaces spaced from the bearing surfaces and defining a gap therebetween for receiving a gas seal, the inner nozzle band assembly including a radially inwardly extending circumferential flange and the engine including an inner support member oriented adjacent the flange and having at least one load bearing surface for mating with and supporting the flange for a limited range of axial displacement, each of the inner nozzle band assembly and the inner support member having respective sealing surfaces spaced from the bearing surface on the inner support member and oriented in opposed relationship for receiving a seal therebetween, and means for releasably attaching the flange on the inner nozzle band assembly to the inner support member for inhibiting radial and circumferential motion of the vane assembly. 
     
     
       9. The apparatus of claim 8 wherein the attaching means allows axial displacement of the vane assembly. 
     
     
       10. The apparatus of claim 9 wherein the attaching means comprises at least a pair of circumferentially spaced pins extending through mating apertures in each of the inner support member and the flange on the inner nozzle band. 
     
     
       11. The apparatus of claim 10 wherein the inner support member includes a circumferential slot and the flange on the inner nozzle band assembly is positioned within the slot with the vane assembly in an assembled position. 
     
     
       12. The apparatus of claim 8 wherein the sealing surface on the inner nozzle band assembly is formed on a forward surface of the flange, the inner support member having a circumferential lip extending radially therefrom substantially parallel with the forward surface of the flange, the inner support member sealing surface being formed on the lip. 
     
     
       13. The apparatus of claim 12 wherein the seal comprises a resilient spring seal. 
     
     
       14. Apparatus for statically determinant mounting of a vane assembly in a gas turbine engine, the vane assembly including at least one vane extending between a radially outer nozzle band and a radially inner nozzle band, the radially outer nozzle band having axially directed load bearing elements on distal ends thereof and the radially inner nozzle band having a pair of spaced load bearing elements thereon, the engine including a radially outer support member positioned to engage the load bearing elements in the radially outer nozzle band when the vane assembly is in an operative position and further including a radially inner support member for engaging the pair of spaced load bearing elements to axially restrain the vane assembly, the inner support member including means for releasably connecting the flange thereto for supporting the vane assembly in radial and circumferential directions and further including seal means operatively coupled between said radially outer nozzle band and said radially outer support member for inhibiting gas flow therebetween, the seal means including a radially outwardly extending flange connected to said radially outer nozzle band and a corresponding flange extending from the engine substantially parallel to said radially outwardly extending flange, a resilient seal being positioned between said radially outwardly extending flange and said corresponding flange.